Control and safe-starting device for use in a detachable missile

ABSTRACT

This invention relates to a safe-starting device for a detachable missile fed with current from a source situated on board a vehicle carrying the missile, by means of a cable connected to a removable terminal. In the actual missile housing between a starting mechanism and a current input fed by said cable, there is a provided a time-delay relay in which the electric current emanating from the carrier vehicle is converted into mechanical energy which actuates a transducer capable of supplying an electric current intended to be used directly or to ensure control of the starting mechanism. This device increases the safety of using detachable missiles while at the same time enabling the length of the feed cable to be reduced.

United States Patent Billot 14 1 June 20, 1972 s41 CONTROL AND SAFE-STARTING 2,786,393 3/1957 Grimes ..s9/1.a11 DEVICE FOR USE IN A DETACHABLE 3,034,471 5/1962 Aschinger. ..174/20 X MISSILE 3,149,568 9/1964 Gerber ...244/3.l2 X 3,518,613 6/1970 Alpert ..89/1.81 l X [72] Inventor: Jean Billet, Levallois, France 73 A Rafa & Cl Primary Examiner-G. R. Simmons e Attorney-Breitenfeld & Levine [22] Filed: May 11, 1970 211 Appl. No.: 36,239 [571 ABSTRACT This invention relates to a safe-starting device for a detachable [30] reign Application Priority Data missile fed with current from a source situated on board a vehicle carrying the missile, by means of a cable connected to May I3, 1969 France ..6915443 a vabl t r inal,

52 us. c1 ..102/70.26A,89/1.8l1, 89/1.5 D In the actual missile housing between a starting mechanism 51 1m. 01 .;....I-"42b 15/00 and a current input fed y said cable, there is 9 provided a 53] Field of Search". 02/70 701 1; 244/312 time-delay relay in which the electric current emanating from 244/315, 3,1 1,2; 1 14/20; 89/13] 1 15; 60/391 82, the carrier vehicle is converted into mechanical energy which 14 actuates a transducer capable of supplying an electric current intended to be used directly or to ensure control of the starting [56] References Cited mechanism.

UNITED STATES PATENTS This device increases the safety of using detachable missiles while at the same time enabling the length of the feed cable to 2,826,120 3/1958 Lang et al. ..s9 1.s be reduwt 2,918,845 l2/1959 Fleming ...89/1.5 D 2,775,745 12/1956 Eaton ..89/l.8l1 10 Claims, 8 Drawing Figures l n i11 T 1 I I 1 111 ikfl 7 I f L 1 1 elk '1 PATENTEnJunzo I972 SHEET 1 0F 4 WMQ JEAN BILLQT PATENTEDJUN 20 I972 SHEET 3 OF 4 TEAM BILLOT Arroeuevs CONTROL AND SAFE-STARTING DEVICE FOR USE IN A DETACHABLE MISSILE BACKGROUND OF THE INVENTION This invention relates to a control and safe-starting device for use in a detachable missile, such as may be borne by a missile. In use, the device is supplied with electric current from a source situated on board the vehicle, e.g., an aircraft, carrying the missile.

In conventional devices of this kind, starting is effected by mechanical pulling using a cable long enough to enable the missile to be started before the cable itself is detached from the carrier vehicle.

The present invention relates to a device which provides greater reliability and which uses an electric cable instead of a pull cord. This obviates the need to use an excessive length of electric cable while enabling the missile to be started at a sufficient distance from the vehicle.

SUMMARY OF THE INVENTION and the vehicle can be interrupted during conversion of the electrical current into mechanical energy, after which the missile works by itself.

The electrical current is preferably converted into mechanical energy through the combustion of a pyrotechnic relay of adjustable duration.

According to the invention, at least two additional safetymeansare preferably provided. The first of these safety means is intended to prevent premature control of the starting mechanism when the missile is on board the carrier vehicle. To this end, there is provided a relaxation unit which only establishes electrical contact between the current source and the input of the definite-time relay when the missile has been detached from the carrier vehicle.

The object of the second safety means is to prevent premature operation, for example as a result of impact, of the transducer forming part of the time-delay relay from supplying current to the starting mechanism. To this end, the device comprises an additional circuit which cuts out the starting mechanism and which comprises a contact enabling the transducer to feed this mechanism only when the first safety means is ensuring supply of the time-delay relay.

The circuit of the device according to the invention can be a single circuit to provide for a single starting, or a multiple-circuit to control several startings or to feed electrically different points, all these controls being incorporated in the missile.

DESCRIPTION OF THE DRAWINGS Other features of the invention, especially as regards the design of the first safety means and the starting mechanism, are shown in the following description in conjunction with the accompanying drawings given by way of example, wherein:

FIG. 1 is a circuit diagram illustrating a device according to the invention.

FIGS. 2 and 3 show respectively in section and in plan a time-delay relay forming part of the device shown in FIG. 1;

FIGS. 4, 5 and 6 show respectively in plan, elevation and in section on the line VI-VI of FIG. 4, a starting mechanism, and

FIGS. 7 and 8 show diagrammatically in section and in plan, respectively, a safety device usable in the circuit shown in FIG. I.

DESCRIPTION OF THE PREFERRED EMBODIMENT The device according to the invention whose circuitry is shown in FIG. I is intended to be incorporated in a detachable missile.

A current input 1 is fed by an electrical cable 2 engaged in a detachable terminal 3 which is arranged on board the vehicle carrying the missile and which is connected to a suitable current source. An electrical circuit 4 connects the current input 1 to a time-delay relay generally denoted by the reference 5. This time-delay relay is capable of supplying an electrical current delivered through a circuit 6 to a starting mechanism denoted generally by the reference 7.

The time-delay relay is shown in more detail in FIGS. 2 and 3. In this relay, the circuit 4 is connected in such a way that it is able to ignite a pellet 8 intended to set light to a pyrotechnic fuse 9 accommodated in a duct 10 formed in the delay housing. This duct 10 is extended by a metal bellows 11 in contact with a stop 12 under the action of a spring 13 controlling the positioning of a key 14 having a half-circular cross-sectional shape. In its working position, shown in FIG. 2, this key 14 retains a striker 15 subjected to the action of a spring 16.

When the pyrotechnic charge 9 burns, the bellows 11 is extended under the effect of the gases so that the stop 12 under the action of the spring 13 is displaced correspondingly, as a result of which the key 14 is turned in a clockwise direction in FIG. 2. The key 14 has a suitable flat surface which releases the striker 15 during rotation of the key. Finally, the electrical energy supplied by the circuit 4 is converted into mechanical energy in the form of a displacement of the striker 15 under the effect of the spring 16.

The delay introduced by combustion of the pyrotechnic charge 9 is preferably adjustable. To this end, some of this charge is accommodated in one of the cavities 17, 18, 19, etc. and has a combustion time varying from cavity to another, the aforementioned cavities being formed in a component 20 capable of pivoting about a central axis 21. A conventional ball system 22 enables the member 20 to be locked in a position in which one of the cavities 17 to 19 coincides with the duct 10 formed in the housing to ensure pyrotechnic continuity between the pellet 8 and the charge accommodated in the duct 10. The pyrotechnic delay is selected and the pivoting member 20 positioned accordingly before the missile is placed on board the carrier vehicle, alternatively these two operations can be controlled from the cockpit by means of a system on board the vehicle.

The housing of the time-delay relay accommodates a transducer generally denoted by the reference 23 and intended to convert the mechanical energy emanating from displacement of the striker 15 into electrical energy. This transducer 23 may be in the form of a conventional precussion cell in which the action of the striker 15 against a suitable charge promotes fusion of a suitable material which in its new form generates an electrical current.

The current available at the output of the transducer 23 is carried through the circuit 6 to the input 24 of a starting mechanism 7, one embodiment of which is shown in FIGS. 4 to 6. This mechanism performs for example the function of starting when it causes displacement of at least one control rod 25. To this end, this rod is pivotally connected at 26 to the end of a lever 27 which can pivot about a pin 28. The lever 27 is made to rotate by displacement of the rod 29 pivotally connected to this lever at 30 through a screw jack generally denoted by the reference 31. The control of a jack of this kind by an electric current taken from the terminal 24 is known and is effected in known manner through ignition of a pellet which in turn sets light to a pyrotechnic charge which releases the rod of the jack subjected for example to the action of a spring.

In some cases, it may be desirable to provide for a double starting, i.e. displacement of a second control rod 35 in addition to the rod 25. In this case, electric current has to be supplied to a device 36 which provides for engagement through a kinematic chain between the rod and the lever 27 before current is delivered which causes the rod 29 to be displaced, thus pivoting the lever 27. The device 36 contains a pyrotechnic charge 37 which, when it is entrained, causes a piston 38 to be displaced. The displacement of this piston releases a lever 39 pivotally connected at 40 to the rod 35. This lever 39 subjected to the action of a spring 41 is thus able to pivot about a pin 40 and its head 42 in the form of a cap or stirrup engages in the end 43 suitably recessed for this purpose of the lever 27. Accordingly, when the current reaches the jack 31 with a delay attributable to the time-delay relay 5, the rod 29 of this jack causes the lever 27 to pivot about the pin 28, and the pivoting of this lever will cause both the rod 25 and the rod 35 to be displaced.

To deliver current to the device 36 of the starting mechanism, there is provided (FIG. 1) a second electrical circuit 45 starting from the input terminal 46 connected by the cable to the removable terminal 3, this circuit 45 leading directly to the device 36.

According to one aspect of the invention, the device described in the foregoing also comprises two additional safety means.

The first of these two additional safety means is intended to prevent premature control of the starting mechanism while the missile is on board the carrier vehicle. To this end, there is provided a relaxation unit which only closes electrical contacts 48 in the circuit 4 and optionally in the circuit 45 after the missile has been detached from the carrier vehicle. As shown in FIG. 1, this device can comprise a cam 49 in contact with the switch 48 and integral with a lever 50 subjected to the action of a suitable spring in such a way that when the missile is in contact with the carrier vehicle the lever 50 is in its lowered position and when the missile has been detached the lever 50 is able to pivot under the action of the spring, driving the cam 49 which closes the switch 48.

It is also possible in a preferred embodiment to use a relaxation unit of the kind shown in FIGS. 7 and 8. This unit comprises a block 52 which is integral with the engine and which carries fixed contacts such as 53 to which the circuits 4 and 45 are connected. This suitably recessed block contains a movable element 54 subjected to the action of a spring 55 and carryin g a movable contact 56. This member comprises an extension 57 arranged in such a way that, when the missile is anchlored below the carrier vehicle and the upper part 58 of its housing is in contact with the surface of the vehicle, the movable member 54 is lowered. After the missile has been detached, the extension 57 can slide under the action of the spring 55 in an opening formed for this purpose in the upper part of the housing 58 and this relaxation brings the movable contact 56 into contact with the fixed contacts 53, thus closing the circuits 4 and 45.

Thus, it can be seen that the current will not reach the timedelay relay as long as the missile is not detached from the vehicle.

The second safety means is provided to prevent premature percussion of the transducer 23 of the time-delay relay, for example as a result of a shock or impact when no current is flowing through the circuit 4. This additional safety means is arranged in such a way that the current delivered by the transducer 23 is led to a short circuit line instead of to the starting mechanism 7. To this end, the device comprises an additional circuit 60 (FIG. 1) to which the percussion cell 23 can be connected thus disconnecting the mechanism 7. A contact 61 can close either the normal circuit 6 or the branch circuit 60. The contact 61 is actuated by a suitable device 62 fed by a conductor 63 from the output of the contactor 48. While the contractor 48 is not closed, the device 62 keeps the contact 61 in the position which closes the branch circuit 60 in such a way that even if the transducer of the time-delay relay 5 delivers current, this current is not transmitted to the starting mechanism 7. By contrast, when the missile is started, the contacter 48 is closed, and current flows into the device 62 which actuates the contact 61, closing the normal circuit 6.

What is claimed is:

ii. A safe-starting control device for use in a detachable missile adapted to be carried by and detached from a vehicle, the vehicle having a source of electric power and an electric cable detachably connecting said device to the source, said device serving to control the start of a control mechanism in the missile and comprising:

a. a time-delay relay for connection by said cable to the power source, said relay including means for converting only after a predetermined time delay, an electrical signal received from said source into a mechanical signal,

b. a transducer operatively controlled by said mechanical signal for providing an electrical control signal in response thereto, and

c. a starting mechanism responsive to the electrical control signal from said transducer for controlling the start of the control mechanism,

whereby the cable connection between the vehicle and the detachable engine can be detached after said time-delay relay receives a signal, but the control mechanism will not be started for a predetermined interval after detachment to insure that the vehicle is a safe distance from the missile before the control mechanism starts.

2. A device as defined in claim 1 wherein said time-delay relay includes a pyrotechnic device which is ignited by the electrical signal received from the cable, and a spring-biased striker which is released upon combustion of said pyrotechnic device for a predetermined period.

3. A device as defined in claim 2 wherein the predetermined combustion period of said pyrotechnic device is adjustable.

4. A device as defined in claim 3 wherein said time-delay relay includes a movable member having a plurality of cavities, each of said cavities accommodating at least a portion of said pyrotechnic device, each said portion having a different combustion time, said member being movable to bring any one of said cavities into an operative position wherein the pyrotechnic portion it holds will receive the signal from the cable.

5. A device as defined in claim 1 wherein said transducer is a percussion cell.

6. A device as defined in claim 1 including means for establishing electrical connection between said time-delay relay and the detachable cable only after the missile is detached from the vehicle, said means maintaining said electrical connection open while the missile is attached to the vehicle.

7. A device as defined in claim 6 wherein said means comprises an electrical contact fixed with respect to the detachable missile, a movable contact spring-biased toward said fixed contact, said movable contact having an extension for maintaining said spring depressed and said contacts separated when the detachable missile is attached to the vehicle, said spring moving said movable contact into engagement with said fixed contact when the missile becomes detached from the vehicle.

8. A device as defined in claim 1 including a circuit for shunting an control signal from said transducer around said starting mechanism before said time-delay relay has received an control signal, so that an electrical signal accidentally produced by said transducer as a result of receiving a shock will not operate said starting mechanism, and means for opening said shunt circuit upon receipt of an electrical signal by said time-delay relay.

9. A device as defined in claim 1 wherein said starting mechanism includes a pyrotechnic device which is ignited by the control signal from said transucer, a jack displaced by combustion of said pyrotechnic device, and a pivotally mounted lever pivoted by displacement of said jack, said lever controlling the starting of the control mechanism.

10. A device as defined in claim 9 wherein said starting mechanism includes a second pyrotechnic device for receiving an electrical signal directly from the cable, said direct signal serving to ignite said second pyrotechnic device, and a second lever movable by combustion of said second pyrotechnic device into engagement with said first-mentioned lever for movement by the latter.

or a a e 

1. A safe-starting control device for use in a detachable missile adapted to be carried by and detached from a vehicle, the vehicle having a source of electric power and an electric cable detachably connecting said device to the source, said device serving to control the start of a control mechanism in the missile and comprising: a. a time-delay relay for connection by said cable to the power source, said relay including means for converting only after a predetermined time delay, an electrical signal received from said source into a mechanical signal, b. a transducer operatively controlled by said mechanical signal for providing an electrical control signal in response thereto, and c. a starting mechanism responsive to the electrical control signal from said transducer for controlling the start of the control mechanism, whereby the cable connection between the vehicle and the detachable engine can be detached after said time-delay relay receives a signal, but the control mechanism will not be started for a predetermined interval after detachment to insure that the vehicle is a safe distance from the missile before the control mechanism starts.
 2. A device as defined in claim 1 wherein said time-delay relay includes a pyrotechnic device which is ignited by the electrical signal received from the cable, and a spring-biased striker which is released upon combustion of said pyrotechnic device for a predetermined period.
 3. A device as defined in claim 2 wherein the predetermined combustion period of said pyrotechnic device is adjustable.
 4. A device as defined in claim 3 wherein said time-delay relay includes a movable member having a plurality of cavities, each of said cavities accommodating at least a portion of said pyrotechnic device, each said portion having a different combustion time, said member being movable to bring any one of said cavities into an operative position wherein the pyrotechnic portion it holds will receive the signal from the cable.
 5. A device as defined in claim 1 wherein said transducer is a percussion cell.
 6. A device as defined in claim 1 including means for establishing electrical connection between said time-delay relay and the detachable cable only after the missile is detached from the vehicle, said means maintaining said electrical connection open while the missile is attached to the vehicle.
 7. A device as defined in claim 6 wHerein said means comprises an electrical contact fixed with respect to the detachable missile, a movable contact spring-biased toward said fixed contact, said movable contact having an extension for maintaining said spring depressed and said contacts separated when the detachable missile is attached to the vehicle, said spring moving said movable contact into engagement with said fixed contact when the missile becomes detached from the vehicle.
 8. A device as defined in claim 1 including a circuit for shunting an control signal from said transducer around said starting mechanism before said time-delay relay has received an control signal, so that an electrical signal accidentally produced by said transducer as a result of receiving a shock will not operate said starting mechanism, and means for opening said shunt circuit upon receipt of an electrical signal by said time-delay relay.
 9. A device as defined in claim 1 wherein said starting mechanism includes a pyrotechnic device which is ignited by the control signal from said transucer, a jack displaced by combustion of said pyrotechnic device, and a pivotally mounted lever pivoted by displacement of said jack, said lever controlling the starting of the control mechanism.
 10. A device as defined in claim 9 wherein said starting mechanism includes a second pyrotechnic device for receiving an electrical signal directly from the cable, said direct signal serving to ignite said second pyrotechnic device, and a second lever movable by combustion of said second pyrotechnic device into engagement with said first-mentioned lever for movement by the latter. 